US5758500A - Exhaust gas turbochanger for an internal combustion engine - Google Patents

Exhaust gas turbochanger for an internal combustion engine Download PDF

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Publication number
US5758500A
US5758500A US08/839,351 US83935197A US5758500A US 5758500 A US5758500 A US 5758500A US 83935197 A US83935197 A US 83935197A US 5758500 A US5758500 A US 5758500A
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United States
Prior art keywords
flow
exhaust gas
turbine
turbine wheel
annular sleeve
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Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
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US08/839,351
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English (en)
Inventor
Siegfried Sumser
Horst Hanauer
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Mercedes Benz Group AG
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Mercedes Benz AG
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Assigned to MERCEDES-BENZ AG reassignment MERCEDES-BENZ AG ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: ERFMANN, WOLGANG, FINGER, HELMUT, HANAUER, HORST, SCHMIDT, ERWIN, SUMSER, SIEGFRIED
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Publication of US5758500A publication Critical patent/US5758500A/en
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Assigned to DAIMLER-BENZ AKTIENGESELLSCHAFT reassignment DAIMLER-BENZ AKTIENGESELLSCHAFT MERGER RE-RECORD TO CORRECT THE NUMBER OF MICROFILM PAGES FROM 60 TO 98 AT REEL 9360, FRAME 0937. Assignors: MERCEDES-BENZ AG
Assigned to DAIMLERCHRYSLER AG reassignment DAIMLERCHRYSLER AG MERGER (SEE DOCUMENT FOR DETAILS). Assignors: DAIMLER-BENZ AKTIENGESELLSCHAFT
Assigned to DAIMLERCHRYLER AG reassignment DAIMLERCHRYLER AG CHANGE OF NAME (SEE DOCUMENT FOR DETAILS). Assignors: MECEDES-BENZ AG
Assigned to DAIMLER AG reassignment DAIMLER AG CHANGE OF NAME (SEE DOCUMENT FOR DETAILS). Assignors: DAIMLERCHRYSLER AG
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/167—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes of vanes moving in translation
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/141—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of shiftable members or valves obturating part of the flow path
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B37/00—Engines characterised by provision of pumps driven at least for part of the time by exhaust
    • F02B37/02—Gas passages between engine outlet and pump drive, e.g. reservoirs
    • F02B37/025—Multiple scrolls or multiple gas passages guiding the gas to the pump drive
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B37/00—Engines characterised by provision of pumps driven at least for part of the time by exhaust
    • F02B37/12—Control of the pumps
    • F02B37/24—Control of the pumps by using pumps or turbines with adjustable guide vanes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/40—Application in turbochargers
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T10/00—Road transport of goods or passengers
    • Y02T10/10—Internal combustion engine [ICE] based vehicles
    • Y02T10/12—Improving ICE efficiencies

Definitions

  • the invention relates to an exhaust gas turbocharger for an internal combustion engine with radial and semi-axial flow passages leading to the turbine wheel from a circumferential flow channel by way of annular nozzle structures including guide vanes with an adjustable flow cross-section.
  • U.S. Pat. No. 5,454,225 which is assigned to the assignee of the present application discloses an exhaust gas turbocharger for an internal combustion engine.
  • the turbocharger includes a single flow duct with radial and semi-radial flow passages guiding the exhaust gas from a flow duct extending around the turbine rotor onto the rotor.
  • the radial flow passages include controllable guide vanes by which the flow cross-section is adjustable.
  • the annular flow passages are in the form of annular nozzles provided by a ring structure which is mounted on the guide vanes of one of the flow passages.
  • the exhaust turbine includes radial and semi-axial flow passages through which the exhaust gas is conducted to the turbine wheel and which are separated by a guide ring, and an annular sleeve is mounted in the turbine housing so as to be slideable therein along the axis of the turbine wheel for closing the radial flow passage of the turbine.
  • part of the flow cross-section can be blocked by the sleeve structure such that, especially with small mass flows, there are relatively little mismatched incident flow losses at the turbine wheel entrance.
  • it provides for only small flow separation zones whereby the turbine efficiency is substantially improved particularly in that operational range.
  • the single-flow turbine housing can be relatively large whereby low flow speeds can be maintained in its flow passages and, consequently relatively low flow losses will occur.
  • the gas flow is accelerated within the relatively short length of the guide vane structures whereby advantageous turbine operational efficiencies can be obtained for the various flow guide vane positions.
  • the single flow turbine housing may be of special shape or it may simply be a gas collecting chamber from which the gas under pressure enters the flow guide structure.
  • the annular sleeve is so designed that it can firmly engage the flow guide ring with its front end so that it can fully close the flow cross-section of the turbine inlet passage to the turbine wheel with the exception of some leakage flow. This provides for further improvement of the non-stationary and the consumption behavior of the engine as the flow through one of the annular nozzles can be fully blocked.
  • the annular sleeve is provided, at its front end preferably with an annular blade structure and the flow guide ring has a recess in which the annular blade structure is received when the annular sleeve is in the turbine inlet closing position.
  • the arrangement is such that the front end of the annular blade structure remains slightly within the recess even when the annular sleeve is fully retracted so as to provide support for the annular blade structure and prevent cogging during axial movement of the annular blade structure into the recess.
  • annular radial inlet nozzle structure When the annular blade structure is fully received in the recess the annular radial inlet nozzle structure is fully closed. This improves engine operation particularly at low mass flows. The whole exhaust gas flow then passes through the partially axial inlet nozzle structure which includes flow guide baffles designed for a smaller mass flow whereby the unstationary and consumption behavior of the engine is improved.
  • FIGURE is a cross-sectional view of an exhaust gas turbocharger according to the invention.
  • the turbocharger as shown in the FIGURE comprises a housing 1 with a turbine section 2 and a compressor section 3 arranged in a well known manner.
  • a single flow spiral compressor housing 3a with a flow channel 4 is attached to the housing 1 and a radial impeller 5 is disposed in the compressor housing 3a.
  • the housing 1 carries a single-flow spiral turbine housing 2a with a gas flow channel 6 disposed around a turbine wheel 7 through which exhaust gas flows in a radial and halfway axial direction and which is part of the turbine section 2.
  • the turbine wheel 7 has a radial flow entrance area 7a and a halfway axial entrance area 7b.
  • the radial impeller 5 and the turbine wheel 7 are mounted on a common shaft 8 which is supported in the housing 1 by radial bearings 9 and 10.
  • the single flow spiral flow channel 6 comprises a channel 11 from which the exhaust gas flow is admitted to the turbine wheel 7 by way of an annular nozzle structure 12 with annular nozzles 12a and 12b providing for a radial and a halfway axial flow passage.
  • the flow channel 6 includes at its end adjacent the housing 1 a cone-shaped border element 13 which is mounted on the housing 1 by bolts 14 and which has a central opening through which the shaft 8 extends.
  • the annular nozzle structure 12 is divided by a flow guide ring 15 into a radial annular nozzle 12a and a halfway axial annular nozzle 12b.
  • the flow guide ring 15 is supported on a guide blade structure 16 firmly connected to the cone-shaped border element 13 and to the flow guide ring 15. It has an outer shape formed in axial symmetry with respect to the axis 17 of the turbine wheel 7.
  • the guide blade structure 16 is arranged closely adjacent the end face 7c of the turbine wheel 7 and has a narrow flow guide blade cross-section with blades which are optimized for low to medium exhaust gas mass flows.
  • annular sleeve 18 which is supported in the turbine section 2 so as to be slideable therein in the direction of the turbine wheel axis 17.
  • the annular sleeve 18 carries a guide blade ring 20 which is mounted thereon for example by friction welding.
  • the annular sleeve 18 comprises a cylindrical section 18a on which the guide blade ring 20 is mounted and which is movable over the turbine wheel 7 with only a small clearance therebetween and has, downstream of the turbine wheel 7, a slightly conical section 18b which forms a diffuser extending from the cylindrical section 18a in downstream direction of the turbine wheel 7.
  • the diameter of the section 18b increases with increasing distance from the turbine wheel 7. Any flow separation occurring at the circumferential edge 29 of the annular sleeve 18 adjacent the turbine wheel periphery 7d is kept very small because of the small diffuser opening 18b of the annular sleeve 18.
  • the annular sleeve 18 is slideably supported in an exhaust nozzle portion 21 of the turbine housing 2a and is sealed toward the gas flow channel 6 of the turbine 2 by two axially spaced seal rings 22, 23.
  • the guide blade ring 20 is disposed in the annular radial nozzle 12a and is movable in the direction of the turbine wheel axis 17, and the adjacent flow guide ring 15 has a radially symmetrical outer shape and is provided recess 24 for receiving the guide blade ring 20. With the movable guide blade ring 20 the flow cross-section 25 of the annular radial nozzle 12a can be controlled.
  • the recess 24 in the flow guide ring 15 which receives the guide blade ring 20 is preferably an annular groove extending axially into the flow guide ring 15 and the guide blade ring 20 preferably has an end disc disposed at its free end by which it is supported in the guide ring groove.
  • the annular sleeve 18 is moved inwardly until the front end 19 of the annular sleeve 18 engages a stop 26 of the flow guide ring 15 (this position being shown by a dashed line). In this position of the annular sleeve 18 the guide blade ring 20 is fully received in the recess 24 of the flow guide ring 15 and the radial flow entrance area 7a is closed except for some leakage flow.
  • the annular sleeve 18 When the exhaust gas mass flow increases and the radial flow entrance area 7a is to be opened, for example with full engine load, the annular sleeve 18 is moved axially outwardly into the position as shown in the FIGURE such that the front end 19 of the annular sleeve 18 is in radial alignment with a nose portion 27 of the turbine housing 2a defining the narrowest flow path between the flow guide ring 15 and the turbine housing 2a. In this position of the annular sleeve 18 only the guide blade ring 20 is disposed in the annular nozzle 12a.
  • the guide blade ring 20 and the recess 24 of the flow guide ring 15 are so dimensioned that, in this position of the annular sleeve 18, a portion 28 of the guide blade ring 20 remains within the recess 24 of the flow guide ring 15 in order to prevent jamming of the guide blade ring 20 when it is inserted into the recess 24 in the flow guide ring 15.
  • the recess 24 in the flow guide ring 15 is shown as an annular groove the flow guide ring 15 may have separate axial pockets in which the blades of the flow guide ring are received and which are separated by web portions extending between adjacent pockets.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Supercharger (AREA)
  • Control Of Turbines (AREA)
US08/839,351 1996-04-18 1997-04-17 Exhaust gas turbochanger for an internal combustion engine Expired - Lifetime US5758500A (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19615237A DE19615237C2 (de) 1996-04-18 1996-04-18 Abgasturbolader für eine Brennkraftmaschine
DE19615237.2 1996-04-18

Publications (1)

Publication Number Publication Date
US5758500A true US5758500A (en) 1998-06-02

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
US08/839,351 Expired - Lifetime US5758500A (en) 1996-04-18 1997-04-17 Exhaust gas turbochanger for an internal combustion engine

Country Status (3)

Country Link
US (1) US5758500A (fr)
EP (1) EP0802305B1 (fr)
DE (2) DE19615237C2 (fr)

Cited By (31)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2000047873A1 (fr) * 1999-02-11 2000-08-17 Daimlerchrysler Ag Turbocompresseur pour moteur a combustion interne
US6220031B1 (en) * 1998-08-26 2001-04-24 Daimlerchrysler Ag Exhaust gas turbocharger for an internal-combustion engine and method of operating same
US6220032B1 (en) * 1998-09-29 2001-04-24 Daimlerchrysler Ag Engine braking process for a supercharged internal-combustion engine
US6314736B1 (en) * 1999-12-21 2001-11-13 Daimlerchrysler Ag Exhaust gas turbine of a turbocharger for an internal combustion engine
WO2002031384A2 (fr) 2000-10-06 2002-04-18 Honeywell International Inc. Presse-etoupe annulaire destine a un turbocompresseur
US6543221B1 (en) * 1998-08-26 2003-04-08 Zeuna-Staerker Gmbh & Co. Kg Device for stabilizing the flow in the exhaust line of an internal combustion engine
US20030230085A1 (en) * 2000-09-29 2003-12-18 Siegfried Sumser Exhaust gas turbocharger, supercharged internal combustion engine and method of operation
US20040025504A1 (en) * 2000-11-30 2004-02-12 Perrin Jean-Luc Hubert Variable geometry turbocharger with sliding piston
US20040062638A1 (en) * 2002-06-22 2004-04-01 Siegfried Sumser Turbine for an exhaust gas turbocharger
US6715288B1 (en) * 1999-05-27 2004-04-06 Borgwarner, Inc. Controllable exhaust gas turbocharger with a double-fluted turbine housing
WO2005106210A1 (fr) * 2004-05-03 2005-11-10 Honeywell International Inc. Turbocompresseur a gaz d'echappement dote d'une bague coulissante reglable
US20050260068A1 (en) * 2004-05-18 2005-11-24 C.R.F. Societa Consortile Per Azioni Automotive compressor
US20050268610A1 (en) * 2002-08-16 2005-12-08 Helmut Daudel Exhaust gas turbocharger for an internal combustion engine
US20070031261A1 (en) * 2003-02-19 2007-02-08 Alain Lombard Turbine having variable throat
US20070209361A1 (en) * 2006-03-08 2007-09-13 Pedersen Melvin H Multiple nozzle rings and a valve for a turbocharger
US20080223039A1 (en) * 2005-09-29 2008-09-18 Siegfried Sumser Internal combustion engine having two exhaust gas turbochargers connected in series
US20090151350A1 (en) * 2005-04-04 2009-06-18 Dominique Petitjean Variable Flow Turbocharger
US20090290980A1 (en) * 2008-05-20 2009-11-26 Mitsubishi Heavy Industries, Ltd. Mixed flow turbine
US20100260595A1 (en) * 2008-03-27 2010-10-14 International Engine Intellectual Property Company, Llc Flow regulation mechanism for turbocharger compressor
EP2400127A1 (fr) * 2009-02-18 2011-12-28 Mitsubishi Heavy Industries, Ltd. Turbocompresseur
US20120099965A1 (en) * 2009-07-02 2012-04-26 Borgwarner Inc. Turbocharger turbine
US8250760B2 (en) 2004-05-03 2012-08-28 Honeywell International Inc. Center housing of a turbine for a turbocharger and method of manufacturing the same
US20130129497A1 (en) * 2010-08-05 2013-05-23 Borgwarner Inc. Exhaust-gas turbocharger
US20140208741A1 (en) * 2013-01-31 2014-07-31 Electro-Motive Diesel, Inc. Turbocharger with axial turbine stage
US20140219786A1 (en) * 2011-10-08 2014-08-07 Zhifu ZHU Volute device for turbine
CN104718361A (zh) * 2013-09-11 2015-06-17 三菱重工业株式会社 涡轮增压机、涡轮喷嘴及船舶
US20160186568A1 (en) * 2013-06-13 2016-06-30 Continental Automotive Gmbh Turbocharger With a Radial-Axial Turbine Wheel
US20170356333A1 (en) * 2014-11-19 2017-12-14 Brunel University London Variable geometry turbocharger turbine
US20180016942A1 (en) * 2015-03-05 2018-01-18 Mitsubishi Heavy Industries, Ltd. Turbocharger
CN110475945A (zh) * 2017-04-13 2019-11-19 Abb涡轮系统有限公司 用于废气涡轮增压器的喷嘴环
US11220957B2 (en) * 2018-06-27 2022-01-11 Ihi Charging Systems International Gmbh Exhaust gas turbocharger

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DE10029640C2 (de) * 2000-06-15 2002-09-26 3K Warner Turbosystems Gmbh Abgasturbolader für eine Brennkraftmaschine
DE10029807C1 (de) * 2000-06-16 2002-03-21 Daimler Chrysler Ag Abgasturbolader für eine Brennkraftmaschine
DE10212675B4 (de) 2002-03-22 2006-05-18 Daimlerchrysler Ag Abgasturbolader in einer Brennkraftmaschine
DE10253693B4 (de) * 2002-11-18 2005-12-01 Borgwarner Turbo Systems Gmbh Abgasturbolader
EP1433937A1 (fr) 2002-12-23 2004-06-30 BorgWarner Inc. Turbocompresseur avec la dérivation integrée dans le carter et méthode de fabrication
DE10335261A1 (de) 2003-08-01 2005-02-17 Daimlerchrysler Ag Verdichterrad und/oder Turbinenrad für eine Sekundärluftfördereinrichtung
DE102009004890A1 (de) * 2009-01-16 2010-07-22 Bosch Mahle Turbo Systems Gmbh & Co. Kg Ladeeinrichtung
DE102013006928A1 (de) 2013-04-22 2014-10-23 Volkswagen Aktiengesellschaft Abgasturbolader
CN110454240B (zh) * 2019-08-28 2024-09-06 天津大学 一种部分进气轴流式超临界二氧化碳透平膨胀机

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EP0051125A2 (fr) * 1980-11-04 1982-05-12 Dr.Ing.h.c. F. Porsche Aktiengesellschaft Turbine d'un turbocompresseur à gaz d'échappement pour moteurs à combustion
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DD126796A1 (fr) * 1976-03-31 1977-08-10
DE2843202A1 (de) * 1978-10-04 1980-04-17 Barmag Barmer Maschf Abgasturbolader fuer brennkraftmaschinen
EP0051125A2 (fr) * 1980-11-04 1982-05-12 Dr.Ing.h.c. F. Porsche Aktiengesellschaft Turbine d'un turbocompresseur à gaz d'échappement pour moteurs à combustion
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EP0678657A2 (fr) * 1988-05-27 1995-10-25 LEAVESLEY, Malcolm George Turbosoufflante
US5025629A (en) * 1989-03-20 1991-06-25 Woollenweber William E High pressure ratio turbocharger
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US5454225A (en) * 1993-09-09 1995-10-03 Mercedes-Benz A.G. Exhaust gas turbocharger for an internal combustion engine

Cited By (55)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6220031B1 (en) * 1998-08-26 2001-04-24 Daimlerchrysler Ag Exhaust gas turbocharger for an internal-combustion engine and method of operating same
US6543221B1 (en) * 1998-08-26 2003-04-08 Zeuna-Staerker Gmbh & Co. Kg Device for stabilizing the flow in the exhaust line of an internal combustion engine
US6220032B1 (en) * 1998-09-29 2001-04-24 Daimlerchrysler Ag Engine braking process for a supercharged internal-combustion engine
US6536214B2 (en) 1999-02-11 2003-03-25 Daimlerchrysler Ag Exhaust gas turbocharger for an internal combustion engine
WO2000047873A1 (fr) * 1999-02-11 2000-08-17 Daimlerchrysler Ag Turbocompresseur pour moteur a combustion interne
US6715288B1 (en) * 1999-05-27 2004-04-06 Borgwarner, Inc. Controllable exhaust gas turbocharger with a double-fluted turbine housing
US6314736B1 (en) * 1999-12-21 2001-11-13 Daimlerchrysler Ag Exhaust gas turbine of a turbocharger for an internal combustion engine
US20030230085A1 (en) * 2000-09-29 2003-12-18 Siegfried Sumser Exhaust gas turbocharger, supercharged internal combustion engine and method of operation
WO2002031384A2 (fr) 2000-10-06 2002-04-18 Honeywell International Inc. Presse-etoupe annulaire destine a un turbocompresseur
WO2002031384A3 (fr) * 2000-10-06 2002-06-20 Honeywell Int Inc Presse-etoupe annulaire destine a un turbocompresseur
US7024855B2 (en) * 2000-11-30 2006-04-11 Honeywell International, Inc. Variable geometry turbocharger with sliding piston
US20040025504A1 (en) * 2000-11-30 2004-02-12 Perrin Jean-Luc Hubert Variable geometry turbocharger with sliding piston
US20040062638A1 (en) * 2002-06-22 2004-04-01 Siegfried Sumser Turbine for an exhaust gas turbocharger
US6834500B2 (en) * 2002-06-22 2004-12-28 Siegfried Sumser Turbine for an exhaust gas turbocharger
US20050268610A1 (en) * 2002-08-16 2005-12-08 Helmut Daudel Exhaust gas turbocharger for an internal combustion engine
US7121788B2 (en) * 2002-08-16 2006-10-17 Borgwarner Inc. Exhaust gas turbocharger for an internal combustion engine
US20070031261A1 (en) * 2003-02-19 2007-02-08 Alain Lombard Turbine having variable throat
US8608433B2 (en) * 2003-02-19 2013-12-17 Honeywell International, Inc. Turbine having variable throat
WO2005106210A1 (fr) * 2004-05-03 2005-11-10 Honeywell International Inc. Turbocompresseur a gaz d'echappement dote d'une bague coulissante reglable
US8202042B2 (en) 2004-05-03 2012-06-19 Honeywell International Inc. Exhaust gas turbocharger with adjustable slide ring
US8250760B2 (en) 2004-05-03 2012-08-28 Honeywell International Inc. Center housing of a turbine for a turbocharger and method of manufacturing the same
US20090003995A1 (en) * 2004-05-03 2009-01-01 Honeywell International, Inc. Exhaust Gas Turbocharger With Adjustable Slide Ring
US20050260068A1 (en) * 2004-05-18 2005-11-24 C.R.F. Societa Consortile Per Azioni Automotive compressor
US7374398B2 (en) * 2004-05-18 2008-05-20 C.R.F. SOCIETá CONSORTILE PER AZIONI Automotive compressor
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Publication number Publication date
DE19615237A1 (de) 1997-10-23
EP0802305B1 (fr) 2000-05-31
EP0802305A1 (fr) 1997-10-22
DE59701800D1 (de) 2000-07-06
DE19615237C2 (de) 1999-10-28

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